Aircraft control



'Jn.25,1944. L.A.sHETLER AIRCRAFT CONTROL Filed Feb. 21, 1941 s sheets-sheet 2 r) .f/v M A. um e. l mw L N .hm

Jan. 25, 1944. A. sH'E'rLER AIRCRAFT CONTROL Filed Feb. 21. V1941 3 Sheets-Sheet 3 me 1m 2s 19441 2,339,955 L UNITED. STATES PATENT 'o'Fric-af,

mohisnmor.'

Lewis A. Slietler,` Omaha, Nebr. assigner to Morton Aircraft Corporation, Omaha, Nebr,

Application February 21, 1941, serian No. 380,052

' 1 claim. (cl. 244-83) My invention is directed to anaircrai't control ing provided with sleeves I 9 xed to thelower unit and has as one of the principal objects ends of hollow shafts 2li respectively. The shafts thereof the provision of a control unit so conare rotatably mounted within hollow columns structed and arranged as to be readily accessible 2l respectively, the latter being xed to the il to the pilot at all times and which requires a minimum amount of operating space, in Figures 1 and 2 of the drawings. Juxtaposi- Another object of my invention is to provide tioned with respect to the adjacent column 2i, a device of the above described character) so conis a reciprocating elevator control rod 23, the latstructed and arranged as to permitloperation of ter, together with the adjacent shaft 2B and colthe ailerons and elevator independently of each 1o umn 2l constituting parts of a control unit A a other and regardless of their respective positions. pair of said units being employed for the pur- An important object ofmy invention is propose of permitting` dual control of the aircraft vide a device of the character described which is as clearly illustrated in the drawings. simple in construction, durable in use, e'lcient The lower end of each rod 23 is pivotally conin operation and economical in manufacture. 15 nected as at 2t to a subjacent ZygOn or cross Other objects and advantages will be apparent bar of a yoke 25, the upper ends of the sides from the following description, appended claim 2l. of said yoke 2S being pivotally. connected to and annexed drawings. bearings 28 mounted on the aircraft prejacent Referring to the drawings wherein like reierthe instrument panel 22. `Interiacent the ends ence characters designate like parts throughout 2o thereof, the cross bar 25 has fixed thereto the the several views: upper end of a downwardly extending arm 2d.

Figure l is a fragmentary top plan view, partly the lower end of said arm 29 being pivotally in section, of en aircraft; and illustrating my inconnected, as at B. to the front end of a shaft vention as applied thereto. 3|, the latter being slidably mounted within the Figure 2 is a side elevation of the structure 25 shaft I 3.

disclosed m Figure 1 l. 'I'he rear end of the shaft 3| is connected as' at Figure 3 is a sectional view taken' on the line 32, to the front end of anauxiliary shaft 3%, the

3 3 0f Figure 2. latter having its rear end'pivotally connected, by Figure 4 is a sectional view taken on the line a D811' 0f links 34, to thev lower end of a rocher s aof Figure 2. 30 arm 3E. The upper end of the rocker arm Se Figure 5 is e, seraient-i1 view taken on the line l is iixed to a transverse rock shaft 36 connected 5 5 of Figure 2, to the lateral sections tl of an elevator whereby Figure 6 is a sectional view taken on the line t0 effect unitary DiVOtiDg 0r rocking of sold Secof Figure 1 tions of the elevator. Obviously, rotation of the .As illustrated in the drawings I` provide a pair Shaft i3 by one of the shafts 2@ effects pivoting of ailerons 5 equipd with transversely extendof the ailerons while reciprocation of one of the ing rock shafts or torque tubes 6 having xed to rods 23 effects rocking or pivoting of the elevator their inner ends links l, the latter having` pivotthrough the medium 0f their respective Shafts ally connected thereto universal joints carried 3 mld 3L on the outer ends of rods s, the inner ends of the InSmllCh as Sash 0i the control units A are latter having connected thereto universal joints 0f an identical construction adetail description e@ mounted on the outer ends of a pair grietof one will sumce, it being understood that the erally and oppositely extending arms il. vThe b reference characters indicative of parts of one inner ends of the arms il are iixed to a collar unit are indicative of like parte of the other um@ l2 carried on the rear end of a forwardly ex- 45 Eah mit A omplses Steering or control wheel tending hollow shaft i3. The front end of the 4G provided with a hub 'ci formed with acenshait I3 has fixed thereto a collar it provided trally disposed boss e2 having riveted thereto a with oppositely disposed ears to which are conbearing plate or disk $3. the latter being of a nected universal joints lo ixed on the inner ends materially greater diameter than said boss to proof a pair of laterally and upwardly extending 5o vide a circumferentially disposed marginal porrods is respectively. tion extending about and away from sam bess `The outer ends of the rods IS are provided and which marginal portion is rotatably mounted with universal joints connecting said rods tothe within a sectional bearing dt, the latter having inner ends of inwardly and downwardly extendupper and lower sections and with the upper ,seem ing arms le, the outer ends o said arms it betion overlying the merel portion of the pian lmembers I pivotally connected to similar'members 46 fixed to the upper end of the column 2l.

' The lower section of the bearing M is provided with a bifurcated ear 41 having pivotally connected therein the upper end of the rod 23. Obviously, fore and aft movement of the wheel 40 serves to eiect reciprocation of the rod 23 and operation of the elevator through the 'medium of the shaft 3l and associated parts. Centrally fixed to the hub 4I and plate 43 is the upper end of a universal joint 48, the lowerl end of said joint being xed to the upper end of the shaft 20. Obviously, by rotating the wheel l0 with respect to the bearing 44 and column 2|, operation of the ailerons 5 is effected through the medium of the shaft I3 and associated parts. From the foregoing, it will be apparent that the elevator and ailerons may be independently operated regardless of their positions with respect to each other. It will also be apparent that I have provided a, simple and efcient control means for operating the ailerons and'elevator of an aircraft and which requires a minimum of operating -spac Without further elaboration the foregoing will so fully explain the invention that others may, by applying current knowledge, readily adapt the same for use under various conditions of service. Moreover, it is not indispensable that all thefeatures of the invention be used conjointly since they may be employed advantageously in various combinations and sub-combinations.

It is obvious that the invention is not coniined to the herein described use therefor as it may be utilized for any purpose to which it is adaptable. It is therefore to be understood that the invention is not limited to the specific construction as illustrated and descrbed'as the same is only illustrative of'the principles of operation, which are capable of extended application in various forms, and that the invention comprehends all construction within the scope of the appended claim.

What I claim is:

In a steering mechanism for aeroplanes, a xed hollow column, a shaft journaled in the column, means connecting said shaft to ailerons, rigid opposed arms formed on the column, an annular member pivoted on said arms for a rocking movement and including annular detachably connected sections coacting with each other in providing an annular seat, a steering wheel including a hub having a boss rotatably received within one of the annular sections, a disc secured on the boss and projecting in the annular seat beyond the' hub for rotatably securing the wheel to the annular member and for permitting the wheel to be employed for rocking the anular member on the arms, means connecting the annular member to an elevator, and a universal joint secured to the shaft and to the boss for rotating the shaft by n the-steering wheel.

LEWIS SHETLER. 

